uCRM: undeflected Common Research Model

The zip files below contain the aerodynamics and structural geometries, meshes, and other data files for two open models for high-fidelity wing aerostructural studies.

uCRM-9: A flexible version of NASA’s Common Research Model configuration (https://commonresearchmodel.larc.nasa.gov/)
uCRM-13.5: A higher aspect ratio version for very flexible wing design studies

A full explanation of how these models were developed can be found in reference [1]. If you use the model, please cite the paper.

The goal of these models is to provide a common benchmark for aerostructural analysis and design optimization of transonic flexible wing aircraft. These models were already used in various studies [2-5]. The methods used in these optimizations were originally described in reference [6].

The flight conditions are actual flight conditions and not the CRM wind tunnel conditions, so the Reynolds number differs. The conditions are:

M = 0.85
CL = 0.5
Altitude = 37,000 ft
uCRM-9: Re = 43,130,072 (Re length 7.01 m)
uCRM-13.5: Re = 35,524,500 (Re length 5.77m)

The files include:

Geometry files for the wing-body-tail configuration of each aircraft (IGES/TIN)
Aerodynamic mesh files for the wing-body-tail configuration of each aircraft, both in multi-block and overset format (CGNS)
Structural mesh files for the aluminum wingbox structure including material properties based on a smeared stiffness blade-stiffened panel approach, external control surface and engine masses, and aerodynamic loads for the nominal cruise (BDF)
Reference solutions using the MACH framework and NASTRAN
All units are in SI (kg/m/s)

References:
1. Brooks TR, Kenway GKW, Martins JRRA. Benchmark Aerostructural Models for the Study of Transonic Aircraft Wings. AIAA Journal. 2018 ;56(7):2840-–2855.
2. Kenway GKW, Martins JRRA. Multipoint High-fidelity Aerostructural Optimization of a Transport Aircraft Configuration. Journal of Aircraft. 2014 ;51(1):144–160.
3. Burdette DA, Martins JRRA. Design of a Transonic Wing with an Adaptive Morphing Trailing Edge via Aerostructural Optimization. Aerospace Science and Technology. 2018 ;81:192–203.
4. Burdette DA, Martins JRRA. Impact of Morphing Trailing Edge on Mission Performance for the Common Research Model. Journal of Aircraft. 2019 ;56:369–384.
5. Brooks TR, Martins JRRA, Kennedy GJ. High-fidelity Aerostructural Optimization of Tow-steered Composite Wings. Journal of Fluids and Structures. 2019 .
6. Kenway GKW, Kennedy GJ, Martins JRRA. Scalable parallel approach for high-fidelity steady-state aeroelastic analysis and adjoint derivative computations. AIAA Journal. 2014 ;52(5):935–951.

以下压缩文件包含两套高保真度翼型气动结构研究公开模型的气动学和结构几何形状、网格以及其它数据文件。

uCRM-9：NASA通用研究模型配置的灵活版本（https://commonresearchmodel.larc.nasa.gov/）
uCRM-13.5：适用于非常灵活翼型设计研究的高升力比版本

关于这些模型如何开发的详细说明，请参阅参考文献[1]。若您使用这些模型，请引用该论文。

这些模型的目的是为跨音速灵活翼型飞机的气动结构分析和设计优化提供一个共同基准。这些模型已在各种研究中得到应用[2-5]。这些优化中使用的原始方法已在参考文献[6]中描述。

飞行条件为实际飞行条件，而非CRM风洞条件，因此雷诺数有所不同。条件如下：

马赫数 M = 0.85
升力系数 CL = 0.5
飞行高度 = 37,000英尺
uCRM-9：雷诺数 Re = 43,130,072（雷诺特征长度 7.01米）
uCRM-13.5：雷诺数 Re = 35,524,500（雷诺特征长度 5.77米）

文件包括：

每个飞机翼身尾配置的几何文件（IGES/TIN）
每个飞机翼身尾配置的气动网格文件，包括多块和交错格式（CGNS）
铝制翼盒结构的结构网格文件，包括基于均匀刚度叶片加强面板方法的材料属性、外部控制面和发动机质量，以及巡航状态的气动载荷（BDF）
使用MACH框架和NASTRAN的参考解
所有单位均为国际单位制（kg/m/s）

参考文献：
1. Brooks TR, Kenway GKW, Martins JRRA. Benchmark Aerostructural Models for the Study of Transonic Aircraft Wings. AIAA Journal. 2018 ;56(7):2840-–2855.
2. Kenway GKW, Martins JRRA. Multipoint High-fidelity Aerostructural Optimization of a Transport Aircraft Configuration. Journal of Aircraft. 2014 ;51(1):144–160.
3. Burdette DA, Martins JRRA. Design of a Transonic Wing with an Adaptive Morphing Trailing Edge via Aerostructural Optimization. Aerospace Science and Technology. 2018 ;81:192–203.
4. Burdette DA, Martins JRRA. Impact of Morphing Trailing Edge on Mission Performance for the Common Research Model. Journal of Aircraft. 2019 ;56:369–384.
5. Brooks TR, Martins JRRA, Kennedy GJ. High-fidelity Aerostructural Optimization of Tow-steered Composite Wings. Journal of Fluids and Structures. 2019 .
6. Kenway GKW, Kennedy GJ, Martins JRRA. Scalable parallel approach for high-fidelity steady-state aeroelastic analysis and adjoint derivative computations. AIAA Journal. 2014 ;52(5):935–951.

搜集汇总

背景与挑战

背景概述

该数据集提供了两个开放模型（uCRM-9和uCRM-13.5），用于高保真机翼气动结构研究，包含几何、网格和参考解等文件，旨在为跨音速柔性机翼飞机的分析和优化提供基准。数据集由密歇根大学发布，适用于航空航天工程和多学科设计优化等领域，采用CC BY 4.0许可证。